Angled impingement inserts with cooling features

ABSTRACT

An engine component assembly for impingement cooling. The engine component assembly includes an engine first component having a cooled surface. The engine first component having a flow path on one side of the cooled surface. A second component is a disposed adjacent to the engine first component between the flow path and the engine first component, and has a plurality of openings forming an array through the second component. The cooling flow path passes through the plurality of openings to cool the cooled surface. The second component having a surface facing the cooled surface of the engine first component. A plurality of discrete cooling features that have at least one wall that has a curved cross-section extend from the second component surface into a gap between and toward the cooled surface of the engine first component and defining an array.

BACKGROUND OF THE INVENTION

The technology described herein relates to angled impingement openingsfor reducing or mitigating particulate accumulation. More specifically,present embodiments relate to, without limitation, an array of openingsin an insert of an engine component.

Most operating environments of a gas turbine engine receive particulatematerial into the engine. Such particulate can have various detrimentaleffects in the engine.

The accumulation of dust, dirt or other particulate matter in gasturbine engines or turbo-machinery reduces the efficiency of themachinery, as well as reducing the effectiveness of the cooling whichoccurs within the engine. The particulate may insulate components of theengine which leads to the increasing component temperature therein.Particulate can also block or plug apertures utilized for coolingcomponents within the engine which further leads to decreasedfunctionality or effectiveness of the cooling circuits within the enginecomponents or hardware.

Accumulation of particulate is in part due to stagnation and/orrecirculation of air flow within cooling circuits. Prior efforts toresolve particulate accumulation problems have included additional flowthrough the engine components so as to increase surface cooling. Thishas deemphasized internal cooling feature effectiveness but utilizesmore compressed air which would alternatively be directed into the corefor improving performance and output of the gas turbine engine.

It would be desirable to reduce or eliminate the factors leading to theincreased temperature or decreased cooling effectiveness of the enginecomponents. It would further be desirable to decrease the amount ofparticulate accumulation and decrease stagnation or low momentum of airflow so that particulate does not accumulate in the aircraft engine.

BRIEF DESCRIPTION OF THE INVENTION

According to some embodiments, an engine component assembly forimpingement cooling. The engine component assembly includes an enginefirst component having a cooled surface. The engine first componenthaving a flow path on one side of the cooled surface. A second componentis a disposed adjacent to the engine first component between the flowpath and the engine first component, and has a plurality of openingsforming an array through the second component. The cooling flow pathpasses through the plurality of openings to cool the cooled surface. Thesecond component having a surface facing the cooled surface of theengine first component. A plurality of discrete cooling features thathave at least one wall that has a curved cross-section extend from thesecond component surface into a gap between and toward the cooledsurface of the engine first component and defining an array.

BRIEF DESCRIPTION OF THE DRAWINGS

The above-mentioned and other features and advantages of these exemplaryembodiments, and the manner of attaining them, will become more apparentand the methods and material for forming an angled impingement insertwith cooling features will be better understood by reference to thefollowing description of embodiments taken in conjunction with theaccompanying drawings, wherein:

FIG. 1 is a side section view of an exemplary gas turbine engine;

FIG. 2 is a side section view of a portion of the propulsor including aturbine and combustor;

FIG. 3 is an isometric view of an exemplary nozzle utilized in theturbine;

FIG. 4 is a partial section view of an exemplary angled impingement of asecond component on a first component;

FIG. 5 is a side section view of an alternative embodiment of the angledimpingement structure;

FIG. 6 is a schematic view of the nozzle;

FIG. 7 is a view of various cross-sections of cooling hole openingswhich may be used with instant embodiments;

FIG. 8 is a view of an array including uniformly spaced apertures whichmay or may not be staggered;

FIG. 9 is a view of an array including non-uniformly spaced apertures;

FIG. 10 is a side schematic view of an exemplary embodiment of angledimpingement holes and cooling features located on the insert;

FIG. 11 is a schematic view of an exemplary plurality of angled coolingapertures of an insert including cooling features extending therefrom;

FIG. 12 is a schematic of an exemplary plurality of angled coolingapertures of an insert including a second embodiment of cooling featuresextending therefrom;

FIG. 13 is a bottom view of the plurality of cooling features of FIGS.11 and 12

FIG. 14 is a top view of an array of uniform spacing with coolingapertures impinging upon the cooling features;

FIG. 15 is a side section view of the embodiment of FIG. 14;

FIG. 16 is a top view of an alternate array having uniform spacing andcooling apertures impinging upon the cooled surface of the enginecomponent; and,

FIG. 17 is a side section view of the embodiment of FIG. 16.

DETAILED DESCRIPTION OF THE INVENTION

Reference now will be made in detail to embodiments provided, one ormore examples of which are illustrated in the drawings. Each example isprovided by way of explanation, not limitation of the disclosedembodiments. In fact, it will be apparent to those skilled in the artthat various modifications and variations can be made in the presentembodiments without departing from the scope or spirit of thedisclosure. For instance, features illustrated or described as part ofone embodiment can be used with another embodiment to still yieldfurther embodiments. Thus it is intended that the present inventioncovers such modifications and variations as come within the scope of theappended claims and their equivalents.

Referring now to FIGS. 1-17, various views are depicted which teachimpingement inserts which reduce stagnation regions and therefore,particulate accumulation or build-up within an engine component. As aresult, engine cooling may be improved. Present embodiments relate togas turbine engine components which utilize an insert to provide coolingair along a cooled surface of an engine component. The insert providesan array of cooling holes or apertures which are facing the cooledsurface of the engine component and direct cooling air onto that coolside surface. The apertures may be formed in arrays and are directed atan oblique angle or a non-orthogonal angle to the surface of the insertand further may be at an angle to the surface of the engine componentbeing cooled. Additionally, the insert may include an array of coolingfeatures extending from the insert surface toward, but not touching, thecooled surface of the component. The present embodiments may be appliedto first stage and second stage nozzles for example, as well as shroudhanger assemblies or other components or combinations that utilizeimpingement cooling and/or are susceptible to particulate build-upresulting in reduced cooling capacity, including but not limited tocombustor liners, combustor deflectors and transition pieces. Variouscombinations of the depicted embodiments may be utilized to form theparticulate accumulation mitigation features described further herein.

As used herein, the terms “axial” or “axially” refer to a dimensionalong a longitudinal axis of an engine. The term “forward” used inconjunction with “axial” or “axially” refers to moving in a directiontoward the engine inlet, or a component being relatively closer to theengine inlet as compared to another component. The term “aft” used inconjunction with “axial” or “axially” refers to a direction toward therear or outlet of the engine relative to the engine center line.

As used herein, the terms “radial” or “radially” refer to a dimensionextending between a center longitudinal axis of the engine and an outerengine circumference. The use of the terms “proximal” or “proximally,”either by themselves or in conjunction with the terms “radial” or“radially,” refers to moving in a direction toward the centerlongitudinal axis, or a component being relatively closer to the centerlongitudinal axis as compared to another component. The use of the terms“distal” or “distally,” either by themselves or in conjunction with theterms “radial” or “radially,” refers to moving in a direction toward theouter engine circumference, or a component being relatively closer tothe outer engine circumference as compared to another component.

As used herein, the terms “lateral” or “laterally” refer to a dimensionthat is perpendicular to both the axial and radial dimensions.

All directional references (e.g., radial, axial, proximal, distal,upper, lower, upward, downward, left, right, lateral, front, back, top,bottom, above, below, vertical, horizontal, clockwise, counterclockwise)are only used for identification purposes to aid the reader'sunderstanding of the present invention, and do not create limitations,particularly as to the position, orientation, or use of the invention.Connection references (e.g., attached, coupled, connected, and joined)are to be construed broadly and may include intermediate members betweena collection of elements and relative movement between elements unlessotherwise indicated. As such, connection references do not necessarilyinfer that two elements are directly connected and in fixed relation toeach other. The exemplary drawings are for purposes of illustration onlyand the dimensions, positions, order and relative sizes reflected in thedrawings attached hereto may vary.

Referring initially to FIG. 1, a schematic side section view of a gasturbine engine 10 is shown having an engine inlet end 12 wherein airenters a propulsor 13, which is defined generally by a multi-stagecompressor, including for example a low pressure compressor 15 and ahigh pressure compressor 14, a combustor 16 and a multi-stage turbine,including for example a high pressure turbine 20 and a low pressureturbine 21. Collectively, the propulsor 13 provides power duringoperation. The gas turbine engine 10 may be used for aviation, powergeneration, industrial, marine service or the like. The gas turbineengine 10 is axis-symmetrical about engine axis 26 so that variousengine components rotate thereabout. In operation air enters through theair inlet end 12 of the engine 10 and moves through at least one stageof compression where the air pressure is increased and directed to thecombustor 16. The compressed air is mixed with fuel and burned providingthe hot combustion gas which exits the combustor 16 toward the highpressure turbine 20. At the high pressure turbine 20, energy isextracted from the hot combustion gas causing rotation of turbine bladeswhich in turn cause rotation of a shaft 24.

The engine 10 includes two shafts 24, 28. The axis-symmetrical shaft 24extends through the turbine engine 10, from the forward end to an aftend for rotation of one or more high pressure compressor stages 14. Theshaft 24 is supported by bearings along its length. The shaft 24 may behollow to allow rotation of the second shaft 28, a low pressure turbineshaft therein. The shaft 28 extends between the low pressure turbine 21and a low pressure compressor 15. Both shafts 24, 28 may rotate aboutthe centerline axis 26 of the engine. During operation the shafts 24, 28rotate along with other structures connected to the shafts such as therotor assemblies of the turbine 20, 21, compressor 14, 15 and a turbofan18 in order to create power or thrust depending on the area of use, forexample power, industrial or aviation.

Referring still to FIG. 1, the inlet 12 includes the turbofan 18 whichincludes a circumferential array of exemplary blades 19 extendingradially outward from the root. The turbofan 18 is operably connected bythe shaft 28 to the low pressure turbine 21 and creates thrust for theturbine engine 10.

Within the turbine areas 20, 21 are airfoils which are exposed toextremely high temperature operating conditions. It is desirable toincrease temperatures in these areas of the gas turbine engine as it isbelieved such increase results in higher operating efficiency. However,this desire to operate at high temperatures is bounded by materiallimitations in this area of the engine. Turbine components are cooled tomanage these material limits. For example, shrouds adjacent to rotatingblades of the turbine or compressor may require cooling. Additionally,nozzles which are axially adjacent to the rotating blades may alsorequire cooling. Still further, the combustor structures which hold theflame and combustion product gases may be cooled with impingementcooling. These components are collectively referred to as first enginecomponents.

Referring now to FIG. 2, a side section view of a combustor 16 and highpressure turbine 20 is depicted. For example, one skilled in the artwill realize upon review of this disclosure that the impingementembodiments defined by first and second components may be used in thearea of the deflector 16 a, which includes a first component 430 and asecond component 450, or the combustor liner 16 b, which includes afirst component 530 and a second component 550.

The turbine 20 includes a number of blades 19 which are connected to arotor disc 23 which rotates about the engine center line 26 (FIG. 1).Adjacent to the turbine blades 19 in the axial direction, the firstengine component may be embodied by the first stage nozzle 30 which isadjacent to the rotating blade 19 of turbine 20. The turbine 20 furthercomprises a second stage nozzle 32 aft of the blade 19. The second stagenozzle 32 may also embody the first engine component as describedfurther herein. The nozzles 30, 32 turn combustion gas for delivery ofthe hot working fluid to the turbine to maximize work extracted by theturbine 20, 21. The nozzle 30 includes an outer band 34, an inner band38 and an airfoil 36. A cooling flow 40 passes through the airfoil 36 tocool the airfoil as combustion gas 41 passes along the exterior of thenozzle 30. One area within a gas turbine engine where particulateaccumulation occurs is within the nozzle 30, 32 of the turbine 20. Theinternal cooling flow 40 which reduces temperature of the components canaccumulate particulate and decrease cooling. The exemplary nozzle 32 mayacquire particulate accumulation and therefore, mitigation featuresdescribed further herein may be utilized in a high pressure turbinestage one nozzle 30 or stage two nozzle 32. However, this isnon-limiting and the features described may be utilized in otherlocations as will be discussed further. Additionally, as describedfurther, shroud assembly 51 may require cooling due to the turbineoperating conditions.

Referring now to FIG. 3, an isometric view of an exemplary nozzle 30 isdepicted. The nozzle includes the outer band 34 and the inner band 38,between which an airfoil 36 is located. The airfoil 36 may be completelyor at least partially hollow and provide the air flow path or flow 40(FIG. 2) through such hollow portion of the airfoil. The airfoil 36includes a leading edge 37, a trailing edge 39 and a radially outer endand radially inner end. The outer surface of the nozzle receivescombustion gas 41 (FIG. 2) from the combustor 16 (FIG. 1). The innersurface of the airfoil 36 is cooled by the cooling flow 40 to maintainstructural integrity of the nozzle 30 which may otherwise be compromisedby the high heat in the turbine 20. The outer band and inner band arelocated at the outer end and inner end of the airfoil, respectively.

The exterior of the airfoils 36 may be formed with a plurality ofcooling film holes 42 which form a cooling film over some or all of theairfoil 36. Additionally, the airfoil 36 may include apertures 43 at thetrailing edge 39.

Referring now to FIG. 4, a partial section view of the nozzle 30 isdepicted through a radial section to depict the interior area of theairfoil 36. In this view, the inner or cooling surface of the airfoil 36is shown. The inner surface 44 is disposed adjacent to the cooling flow40. As used with respect to the cooling flow path, the term “adjacent”may mean directly near to or indirectly near to. Within the airfoil 36is an insert 50 which receives air flow 40 through the hollow space ofthe airfoil 36 and directs the air flow outwardly to an interior surfaceof the airfoil 36. An insert 50 may be inserted inside anothercomponent, or being inserted between two parts. The insert 50 is madewith multiple cooling holes or apertures 52 that allow fluid to flowthrough the insert. Further, the inserts 50 may be generally sealedaround a perimeter to the part being cooled, and therefore, all of thefluid flows through the holes and none goes around the insert.Alternatively, the insert may not be completely sealed and thereforeallows some preselected amount of cooling flow 40 air to bypass theimpingement holes 52. The insert flow area and pressure ratio is suchthat the fluid is accelerated through each impingement cooling hole oraperture 52 to form a cooling impingement jet. The insert 50 is disposedadjacent to the cooling flow 40, between the cooling flow 40 and theinterior airfoil surface 44 according to one embodiment. The insert 50includes a plurality of cooling holes or openings 52. The insert 50directs such cooling air to the airfoil 36 by way of the plurality ofopenings or cooling holes 52 located within the insert 50. The openings52 define at least one array 54. The term “array” is utilized to includea plurality of openings which may be spaced both uniformly from oneanother and non-uniformly at varying distances. An array 54 of holes andapertures, i.e., openings 52, formed in an insert 50 is present if in atleast the two-dimensional case, e.g. a plane, it requires both X and Ycoordinates in a Cartesian system to fully define and locate the holeplacements with respect to one another. Thus an array requires therelative spacings in both dimensions X and Y. This plane example couldthen be understood as applying also to curved inserts as the array islocated on the surface curvature. A grouping of holes or apertures wouldthen comprise any array or a portion of an array, especially if thespacings, hole diameters, orientations, and angles are changing from onehole to another, from one row of holes to another, or even from onegroup of holes to another. A pattern ensues when the same qualifiers arerepeated over a number of holes, rows, or groups. Additionally, thearrays 54 may be arranged in groups or patterns wherein the patterns areeither uniformly spaced or non-uniformly spaced apart.

Each of the openings 52 extends through the insert 50 at a preselectedangle. The angle of each cooling opening may be the same or may vary andmay further be within a preselected range as opposed to a specificangle. For example, the angle may be less than 90 degrees. The openingsmay be in the same or differing directions. The insert 50 directs thecooling air to the cold surface of the airfoil 36, that is the interiorsurface 44 for example, which is opposite the combustion gas or hightemperature gas path 41 traveling along the exterior of the nozzle 30and airfoil 36.

Further, the apertures 52 may be formed in a plurality of shapes andsizes. For example any or various closed boundary shapes may beutilized, including but not limited to circular, oblong, polygon, Bypolygon, any shape having at least three sides and three angles may beutilized. Further, the angles may include radiuses or fillets. Accordingto some embodiments, the apertures are all of a single size. Accordingto other embodiments, the apertures 52 may be of differing sizes.Further, the cross-sectional shapes of the apertures may all be of asingle shape or vary in shape. As shown in FIG. 7, a plurality ofcross-sectional shapes are shown as exemplary apertures 52 which may beutilized. The sizes and shapes may be tuned to provide the desiredcooling or the desired air flow usage through the insert to the insideor cold surface of the airfoil 36. By tuned, it is meant that the sizesand/or shapes may be varied to obtain a desired cooling and/or reductionof particulate build up.

According to the embodiments shown in FIG. 5, an alternate utilizationof the exemplary particulate mitigation structure is provided. Accordingto this exemplary embodiment, a shroud hanger assembly 60 is shownhaving an interior insert 150 which cools a cold side of a shroud by wayof impingement cooling. The shroud hanger assembly 60 comprises a hanger62 that includes a first hanger portion 64 and a second hanger portion66. The hanger portions 64, 66 retain a shroud 68 in position, adjacentto which a blade 19 rotates. It is desirable to utilize cooling fluidmoving within or defining the cooling flow path or circuit to reduce thetemperature of the insert 150 by way of impingement cooling. However, itis known for prior art shroud hanger assemblies to incur particulateaccumulation within this insert area and on the cooling surface of theshroud 68 which over time reduces cooling capacity of the cooling fluid.According to the instant embodiments, the insert 150 may include theplurality of apertures which are angled or non-orthogonal to the surfaceof the insert and surface of the shroud. In this embodiment, the array54 of apertures 52 are angled relative to the surface of the insert andthe opposite surface of the shroud to limit particulate accumulation inthis area of the gas turbine engine.

Referring now to FIG. 6, a schematic view of the angled impingementconfiguration is depicted. The first engine component may be the airfoilnozzle 30 or shroud 68 according to some embodiments. The insert 50, 150may be the second engine component. The angle of the aperture 52 isdefined by an axis 53 extending through the aperture 52. The axis 53 maybe angled with the inner or cooled surface 44 or may be aligned or maybe unaligned with film holes 42. The holes 42 and cooling aperture 52may be aligned where the axis 53 of the cooling aperture passes throughthe cooling film hole 42 or crosses the axis 43 of the cooling film holeat or near the cooling film hole. Alternatively, the axis 53 may not bealigned with the cooling holes 42 so as to impinge the surface 44.

Additionally shown in this view, the relationship of aperture length todiameter ratio may be discussed. The insert 50 may have thicknessgenerally in a horizontal direction for purpose of the description andexemplary depiction. It has been determined that increasing thethickness of the insert may improve the desirable aperturelength-to-diameter ratio which will improve performance. Conventionalinserts have aperture length-to-diameter ratios generally of lessthan 1. For the purpose of generating and forming a fluid jet that has awell-defined core region with minimal lateral spreading, thelength-to-diameter ratios of angled apertures are desired to be in therange of 1 to 10, and more specifically in the range of 1 to 5. Tocomply with other desirable engine metrics such as weight, aperturelength-to-diameter ratios in the range of 1 to 2.5 are frequently moredesirable. The length that is used in this length-to-diameter ratio isdefined as the portion of the aperture centerline axis that maintains acomplete perimeter for the cross-section taken perpendicular to theaxis. Further, the thickness of the insert 50 may be constant or mayvary. Still further, it will be understood by one skilled in the artthat the aperture cross-section may change in area as a function of itslength while keeping the same basic shape, i.e. it may expand orcontract. Accordingly, the aperture axis may define a somewhat orslightly arcuate line, not necessarily a perfectly straight line.

The cooling fluid or cooling air flow 40 is shown on a side of theairfoil 36 and also adjacent to the insert 50, 150. The insert 50includes an array defined by the plurality of apertures 52 located inthe insert and which direct the air outwardly at an angle relative tothe inside surface of the component 50, 150. The nozzle 30 may alsocomprise a plurality of cooling holes 42 which may be at an angle to thesurface as depicted but may be at any angle to the nozzle surface. Withthis embodiment, as with the previous embodiment, the array of coolingopenings may be of various sizes and shapes wherein the apertures may beuniformly spaced or may be non-uniformly spaced and further wherein thepattern or arrays may be uniformly spaced or non-uniformly spaced apart.The cooling apertures 52 may also be of one uniform cross-sectionalshape or of varying cross-sectional shapes and further, may be ofuniform size or varying size or formed in a range of sizes.

Also shown in FIG. 6, is the passage of the cooling flow 40 through oneof the apertures 52. This is shown only at one location for sake ofclarity. The flow of cooling flow 40 is made up of two components. Thefirst axial component 40 a may be an average fluid velocity tangent tothe cooled surface 44. The second radial component 40 b may be anaverage fluid velocity normal to the cooled surface 44. These twocomponents 40 a, 40 b are not shown to scale but define the vector ofthe cooling flow 40 exiting the cooling apertures 52. The components 40a, 40 b may also define a ratio which may be between 0 and 2. Accordingto some embodiments, the ratio may be between 0.3 and 1.5. According tostill further embodiments, the ratio may be between 0.5 and 1.

Additionally, it should be understood by one skilled in the art that thecooling apertures 52, 152 or others described may be aimed in threedimensions although only shown in the two dimensional figures. Forexample, a cooling aperture 52 or any other embodiment in the disclosuremay have an axis 53 which generally represents the cooling flow 40passing through the aperture. The axis 53 or vector of the cooling flow40 through the aperture 52 may be defined by at least two component, forexample a radial component (40 b) and at least one of a circumferentialor axial component (40 a). The vector may be aimed additionally byvarying direction through the third dimension that is the other of thecircumferential or axial dimension, some preselected angular distance inorder to provide aiming at a desired location on the surface of theopposed engine component, or a specific cooling feature as discussedfurther herein. In the depicted embodiment, the third dimension, forexample the circumferential dimension, may be into or out of the page.

Referring now to FIG. 8, a view of an exemplary second component surfaceis depicted, for example component 50 or 150. The surface includes anarray 54 of apertures 52. The array 54 may be formed of rows ofapertures 52 extending in first and second directions. According to oneembodiment, the array 54 is shown having a uniform spacing of apertures52. The apertures 52 in one direction, for example, the left to rightdirection shown, may be aligned or alternatively may be staggered sothat holes in every other row are aligned. The staggering may occur in asecond direction, such as a direction perpendicular to the firstdirection. A plurality of these arrays 54 may be utilized on the insert50 or a mixture of arrays 54 with uniform size and/or shape may beutilized. A single array may be formed or alternatively, or a pluralityof smaller arrays may be utilized along the part. In the instantembodiment, one array 54 is shown with uniform spacing and hole size andshape, on the left side of the figure. On the right side of the figure asecond array is shown with apertures 52 of uniform spacing, size andshape, but the rows defining the array 55 are staggered or offset.

With reference to FIG. 9, a plurality of arrays is again shown. However,in this embodiment the arrays 154 are non-uniformly spaced apart andadditionally, the apertures 52 may be non-uniformly spaced apart. Suchspacing may be dependent upon locations where cooling is more desirableas opposed to utilizing a uniformly spaced array which providesgenerally equivalent cooling at all locations.

The array 154 has a first plurality of apertures 152 which are spacedapart a first distance 153. The apertures 152 are additionally shownspaced apart a second distance 155 which is greater than distance 153.The apertures 152 have a further spacing distance 157 which is greaterthan spacings 153 and 155. All of these spacings are in the firstdirection. Further the spacing of apertures 152 may vary in a seconddirection. For example, the apertures 152 are shown with a first spacing151, 156 and 158 all of which differ and all of which therefore vary rowspacing of the array 154.

Thus, one skilled in the art will appreciate that, regarding theseembodiments, the arrays 154 of apertures 152 may be formed in uniform ornon-uniform manner or a combination thereof. It should be understoodthat non-uniform apertures may form arrays which are arranged ingenerally uniform spacing. Similarly, the apertures may be uniformlyspaced and define arrays which are non-uniform in spacing. Therefore,the spacing of apertures and arrays may or may not be mutuallyexclusive. Still further, the apertures 152 may be formed of same orvarying sizes and cross-sectional areas as previously described.

Referring now to FIG. 10, a side schematic section view is depicted. Theview shows a first engine component 230 spaced from a second enginecomponent 250. The second engine component includes a plurality ofapertures 252 which define an array as described in previousembodiments. The apertures 252 are generic and may be embodied by any ofthe previous embodiments or combinations of embodiments described.

Extending from the inner surface of the component 250, which faces thefirst engine component 230, are a plurality of cooling features 270. Thecooling features 270 interact with the air flow 40 passing through theapertures 252 to create turbulence and vortices in the gap between thefirst and second engine components 230, 250.

Referring now to FIG. 11, a side schematic view of an exemplaryconstruction is provided including first and second engine components230, 250 is depicted. In this view, various embodiments of coolingfeatures 270 are shown and described. The first engine component 230 isshown spaced apart from a second engine component 250. The first enginecomponent 230 may be for non-limiting example a nozzle, a shroud, acombustor liner, combustor deflector or other transition pieces as withprevious non-limiting embodiments. The second engine component 250 mayinclude an insert having a plurality of impingement cooling holes 252including any of the previous embodiments or combinations of previousembodiments. The second engine component 250 is disposed adjacent to thefirst engine component 230, with a gap therebetween, and receivescooling fluid defining a cooling flow 40. The cooling fluid, for examplecompressed air, in the cooling air flow 40 passes through theimpingement cooling holes 252 to the first engine component 230.

In the depicted embodiment, beneath the cooling apertures 252 and spacedopposite the first component 230, which may represent the insert, is thefirst component 230. A hot combustion gas path 41 is shown passing alonga hot surface, for example the lower surface of component 230. The uppersurface of the component 230 is a cooling surface 231 which isimpingement cooled.

The second engine component 250 may further comprise a plurality ofcooling features 270 extending from the second engine component 250toward the first engine component 230. However, the discreet coolingfeatures 270 do not touch the first engine component 230. The coolingfeatures 270 may be arranged as a plurality of fins, for example andwhich may be staggered (offset) or may be aligned along the direction ofcooling flow 40 with the plurality of impingement jets or apertures 252also located in the second engine component 250. In operation, the axesof cooling apertures 252 may be aligned or may be staggered relative tothe discreet cooling features 270 depending on whether the axes of thecooling apertures 252 intersect or impinge on the features 270 or thecooling surface 231 of the first engine component 230.

The first engine component 230 may comprise various structures. Forexample, the first engine component 230 may be a nozzle airfoil aspreviously described or alternatively, may be a turbine shroud.Additionally, the first engine component 230 may comprise portions of acombustor or other engine components and therefore should not beconsidered limited to the parts described herein. The second enginecomponent 250 may comprise a baffle or insert which is located adjacentto the first engine component 230 for providing impingement coolingthereof. During operation, cooling flow 40 moves adjacent to the insert250 and passes through the cooling apertures 252 such that the coolingflow 40 engages the array of cooling features 270 and creates vorticesto provide improved heat transfer while forcing dust and otherparticulate to continue moving along the engine component surface 230rather than adhering thereto. However, it should be understood that itis not necessary that the cooling fluid engage the feature 270initially. In some embodiments, the cooling fluid may impinge the cooledsurface and the post impingement coolant may then engage the features270 which may vary the reaction of the cooling fluid in some manner. Thediscrete cooling features 270 may take various shapes, geometries, formsand various types are shown extending from the surface of component 250into the gap between engine components 230, 250. For example, thecooling features 270 may vary in width or have a constant width.Further, the cooling features 270 may have a length and a height whereinthe length and height are substantially equal or not substantiallyequal. The side view, as shown in FIGS. 10 and 11 depict that thecooling features 270 may include polygonal, cylindrical, triangular orother shapes, any of which may include sharp corners or alternativelymay have curved or radiused corners in order to improve aerodynamics. Bypolygon, it is meant that the cooling features 270 have at least threestraight sides and angles as shown in side view. Further, it should beunderstood that it is also not necessary that edges of features 270 lineup exactly with apertures 252. The features 270 may be staggered oroffset relative to the apertures 252.

Referring now to FIG. 11 and FIG. 13, which depict a bottom view of thediscrete cooling features 270, various embodiments of the discretecooling features 270 are shown depending from the second enginecomponent 250. According to a first embodiment shown at the left side ofthe engine component 250, the cooling feature 272 may be triangularshaped and have a vertical or radial side wall in profile depending fromthe engine component 250. The forward wall 272 a may be semicircular incross-section and depend vertically from the first engine component 250,according to the exemplary orientation depicted. From a lowermost pointof the forward wall 272 a, a second wall 272 b of the cooling feature272 may taper upwardly toward the component surface 250.

The first alternative cooling feature shape 272 has a vertical side wall272 c which may alternatively be linear or curvilinear. The coolingfeature 270 is generally triangular in shape. The forward wall of thetriangular fin 272 may have a wider profile round cross-section and maytaper back in the aft direction to a more narrow profile which may alsohave a round cross-section. Alternatively, the narrow end may be forward(to the left) and may widen moving aft (to the right). The feature 272may be tapered in width to provide the desired aerodynamic effect forthe cooling feature or fin 270.

Referring now to the second cooling feature alternative embodiment, acooling feature 274 is shown depending from the first engine component250. The cooling feature 274 is also triangular in side view or sidesection shape but includes side walls of differing lengths so that thetriangle has different lengths of side wall legs. Whereas the firstembodiment 272 is a right triangle having two equal length sides, thecooling feature 274 is not a right triangle and has different angles ofsides.

Also differing from the first embodiment, side walls 274 c vary in widthbetween a forward end of the feature 274 and an aft end of the feature274. According to the exemplary embodiment, the feature 274 widens fromthe forward end to an intermediate location and narrows between theinner media location and the aft end. The variation of thickness howevermay be formed an alternative configurations. Further, the feature has anupper surface 274 a which depends to a lowermost point at theintermediate location and a second surface 274 b which tapers upwardlyto the aft end. In this embodiment, the intermediate location or lowerpeak of the feature 274 is not centered between the forward end and theaft end. However, such alternative geometry may be utilized.

A third embodiment of the cooling features 276 is generally depicted asan equilateral triangle which depends downwardly from the enginecomponent 250. As discussed previously, the lower peak of the coolingfeature 276 is centered between forward and aft ends. The bottom view ofFIG. 12 shows that the shape of the cooling feature 276 may be conical.However, other shapes may be utilized and these embodiments arenon-limiting and not exhaustive.

Referring now to FIG. 12, additional embodiments of cooling features 270are shown depending from the insert 250 and are described. Theseembodiments differ in side view from the embodiments of FIG. 10.According to instant embodiments, the features 270 have a geometricshape which is other than triangular. For example, the instantembodiments may be rectangular or square in side view.

The side view shows the feature 271 is generally rectangular shaped. Thediscrete cooling feature 271 is shown in FIG. 13 with a forward radiusof a first size and an aft radius of substantially the same size. Whenviewed from below, in FIG. 12, the feature 271 is generally diamondshaped. The forward end and the aft end of the feature 271 extendvertically from the component 230. The cooling feature or fin 271 hasside walls 271 c which increase in thickness from the forward to themiddle location due to the radius of the cross-section at the centrallocation, in the forward to aft (left to right) direction along thefeature 271. Beyond the center location, the feature sidewall 271 ddecreases in thickness to a smaller radius size at the aft end of thefeature 274, where the feature is narrow, as is the forward end. Thus,as compared to the second embodiment 274 wherein the intermediate changein dimension occurred closer to the forward end of the fin and the aftend, the present embodiment 271 has a central location where the featurehas its widest location in the direction of flow 40. However, this isnot limiting as the widest area need not be at the center. As shown inthe side view of FIG. 12, the embodiment looks substantially rectangularin profile as the forward and aft walls are generally vertical. However,it is within the scope of the embodiment that the forward and aft wallsbe angled according to other embodiments described.

Referring to the fifth embodiment of FIG. 12, the side view shows agenerally square or rectangular shaped discrete cooling feature or fin273. The feature 273 has forward wall 273 a is substantially vertical aswith the previous embodiment and the first embodiment. The first wall273 a has a radius dimension providing the round forward end of thefeature 273. The feature 273 further comprises sidewalls 273 b (FIG. 12)which taper back to an aft vertical wall. The aft end may be pointedrather than radiused as in previous embodiments. The embodiment is shownmore clearly in FIG. 13 with the forward dimension of the coolingfeature having a larger radius dimension which decreases down to a pointat the aft end of the fin.

As shown in FIG. 12, the final embodiment is generally cylindricallyshaped cooling feature 275 having a round cross-section. This embodimentmay be defined as a cylindrical structure rather than a fin shape. Aspreviously discussed, these embodiments may be used together or a singleembodiment may be utilized and spaced apart from one another.Additionally, other embodiments are possible wherein combinations offeatures of the various embodiments may be used to form additionaldiscrete cooling features.

Referring again to FIGS. 11-13 collectively, various of the embodimentsof cooling features 270, the cooling air flow 40 is depicted as arrowspassing through the apertures 252. The aiming of the cooling apertures252 may be discussed by the axis of the aperture 252 which correspondsto the depicted arrows representing the fluid flow 40 therethrough. Thecooling features 270 may be oriented in at least two manners relative tothe cooling holes 252. According to some embodiments, the features 270are aligned with the cooling holes 252 wherein the axis of the coolinghole 252 intersects or impinges the features 270. According to alternateembodiments, the features 270 are staggered relative to the coolingholes 252 and offset (into the page) from direct alignment with theapertures 252. In this embodiment, the axis of the cooling holes 252 maynot engage the features 270 but instead, may engage the surface 231 ofcomponent 230, while however still creating flow swirl. Further, thefeatures 270 may be spaced apart uniformly or may be spaced apartnon-uniformly. Still further, the features 270 of the engine component230 may define one or more patterns wherein the multiple patterns may bespaced apart in a uniform manner or may be spaced in a non-uniformmanner in ways previously discussed with the cooling holes.

In the embodiment, where the cooling features 270 are aligned with thecooling features 252, the features 252 may be positioned such that thecooling flow 40 is aligned with the forward walls of the features 270.Alternatively, the cooling air may be directed to engage the lowersurfaces of the cooling features 270. Still further, the cooling air mayengage alternate locations of the cooling features 270.

With reference to FIG. 13, it should also be understood from this view,by one skilled in the art, that the apertures or openings 252 may bemoved relative the embodiments of the cooling features 270. Likewise thecooling features, collectively 270, may be moved relative to theopenings 252. Additionally, the angles of the apertures 252 may bevaried to various non-orthogonal positions to impinge the coolingfeatures 270 at various positions or impinge the opposite surface of theengine component 230. Thus, any or all of these methods of varying theimpingement location may be utilized.

Referring now to FIGS. 14-17, description is provided for the arrays254, 354 which may be defined by apertures of the previous embodimentsin combination with cooling features of the previous embodiments.Referring now to FIG. 14, a top view of an embodiment is shown havingvarious exemplary discussed features desired for use in exemplarycomponents. In the top view, the arrangement of cooling apertures 252are shown in an array 254 wherein the apertures 252 are aligned with thefeatures 270. These features 270 are below the surface of enginecomponent 250 as indicated in FIG. 15, but are shown for purpose ofillustration in this view. The array 254 is defined in this example byan x-axis of first rows and a y-axis of second rows. The array ofapertures 254 is staggered meaning that immediately a first row, forexample in the x-axis direction, is offset by some amount in thex-direction to the adjacent row in the x-direction. The same may be saidfor the rows of the y-direction. In this embodiment the spacing betweenapertures 252 is uniform but alternatively, may be non-uniform aspreviously described.

Referring now to FIG. 15, the side section view of the view of FIG. 14is shown. The apertures 252 are defined in part by axes 253 which alsodefine a direction of flow of cooling fluid through apertures 252. Asdescribed, the features 270 are protruding from the second enginecomponent 250.

According to the instant embodiment, the axis 253 of each of the coolingholes 252 depicts that the impingement point of the cooling flow 40(indicated by axis 353) passing therethrough engages the cooling feature270. This is due to the alignment in the x-direction (FIG. 12) with theaperture axes 253 for impingement of cooling fluid on the features 270.More specifically, the cooling flow 40 engages the forward edge orsurface of the feature 270 at the section cut depicted. However,alternative embodiments may provide that the features 270 are notaligned with the impingement apertures but instead are offset, forexample in the y-direction (FIG. 14) relative to the apertures 253.

With regard now to FIG. 16, a top view of an alternate array 354 isshown. Again the view depicts both the apertures 352 and the features370, which is actually beneath the depicted component 350. The apertures352 are formed in the array 354 which is of uniform spacing, althoughnon-uniform spacing may be utilized as described in previousembodiments. The rows are also staggered and are staggered in the x andy direction. Further however, other embodiments may have rows which arealigned rather than staggered as with the previous embodiment.

With reference now to FIG. 17, a side section view of the embodiment ofFIG. 16 is shown. The array 354 includes apertures 352 located in thefirst component 350. An array is also provided of the cooling features370 which protrude from the second component 330.

In this embodiment, the axes 353 show the direction of cooling flow forthe cooling flow 40 passing through the insert 350 toward the firstengine component 330. In this embodiment, the impingement occurs betweenthe cooling features 370 rather than on the cooling feature as with theembodiment of FIG. 15. As noted previously, the impingement on thesurface 331 may also occur by offsetting the features 370 correspondingto an aperture 352 away from the aperture, for example in they-direction. Additionally, the angle of the aperture axes 253 and 353differ and may provide a further means of adjusting the impingement ofthe axes 253, 353 on or around the features 270, 370.

The foregoing description of structures and methods has been presentedfor purposes of illustration. It is not intended to be exhaustive or tolimit the invention to the precise steps and/or forms disclosed, andobviously many modifications and variations are possible in light of theabove teaching. Features described herein may be combined in anycombination. Steps of a method described herein may be performed in anysequence that is physically possible. It is understood that whilecertain embodiments of methods and materials have been illustrated anddescribed, it is not limited thereto and instead will only be limited bythe claims, appended hereto.

While multiple inventive embodiments have been described and illustratedherein, those of ordinary skill in the art will readily envision avariety of other means and/or structures for performing the functionand/or obtaining the results and/or one or more of the advantagesdescribed herein, and each of such variations and/or modifications isdeemed to be within the scope of embodiments described herein. Moregenerally, those skilled in the art will readily appreciate that allparameters, dimensions, materials, and configurations described hereinare meant to be exemplary and that the actual parameters, dimensions,materials, and/or configurations will depend upon the specificapplication or applications for which the inventive teachings is/areused. Those skilled in the art will recognize, or be able to ascertainusing no more than routine experimentation, many equivalents to thespecific inventive embodiments described herein. It is, therefore, to beunderstood that the foregoing embodiments are presented by way ofexample only and that, within the scope of the appended claims andequivalents thereto, inventive embodiments may be practiced otherwisethan as specifically described and claimed. Inventive embodiments of thepresent disclosure are directed to each individual feature, system,article, material, kit, and/or method described herein. In addition, anycombination of two or more such features, systems, articles, materials,kits, and/or methods, if such features, systems, articles, materials,kits, and/or methods are not mutually inconsistent, is included withinthe inventive scope of the present disclosure.

Examples are used to disclose the embodiments, including the best mode,and also to enable any person skilled in the art to practice theapparatus and/or method, including making and using any devices orsystems and performing any incorporated methods. These examples are notintended to be exhaustive or to limit the disclosure to the precisesteps and/or forms disclosed, and many modifications and variations arepossible in light of the above teaching. Features described herein maybe combined in any combination. Steps of a method described herein maybe performed in any sequence that is physically possible.

All definitions, as defined and used herein, should be understood tocontrol over dictionary definitions, definitions in documentsincorporated by reference, and/or ordinary meanings of the definedterms. The indefinite articles “a” and “an,” as used herein in thespecification and in the claims, unless clearly indicated to thecontrary, should be understood to mean “at least one.” The phrase“and/or,” as used herein in the specification and in the claims, shouldbe understood to mean “either or both” of the elements so conjoined,i.e., elements that are conjunctively present in some cases anddisjunctively present in other cases.

It should also be understood that, unless clearly indicated to thecontrary, in any methods claimed herein that include more than one stepor act, the order of the steps or acts of the method is not necessarilylimited to the order in which the steps or acts of the method arerecited.

In the claims, as well as in the specification above, all transitionalphrases such as “comprising,” “including,” “carrying,” “having,”“containing,” “involving,” “holding,” “composed of,” and the like are tobe understood to be open-ended, i.e., to mean including but not limitedto. Only the transitional phrases “consisting of” and “consistingessentially of” shall be closed or semi-closed transitional phrases,respectively, as set forth in the United States Patent Office Manual ofPatent Examining Procedures, Section 2111.03.

What is claimed is:
 1. An engine component assembly for impingementcooling, comprising: an engine first component having a cooled surface;said engine first component having a flow path on one side of saidcooled surface; a second component disposed adjacent to said enginefirst component between said flow path and said engine first component,said second component having a plurality of openings forming an arraythrough said second component, said cooling flow path passing throughsaid plurality of openings to cool said cooled surface; said secondcomponent having a surface facing said cooled surface of said enginefirst component; a plurality of discrete cooling features extending fromsaid second component surface into a gap between and toward said cooledsurface of said engine first component and defining an array, wherein aforward wall of at least one cooling feature of the plurality of coolingfeatures has a curved cross-section; and said openings extending throughsaid second component at a non-orthogonal angle to said second componentsurface; and wherein the array comprises a staggered array, thestaggered array comprising a first row and a second row, wherein thesecond row is offset by a distance in a first direction from the firstrow.
 2. The engine component assembly of claim 1, wherein the enginefirst component and the second component are parts of a deflector. 3.The engine component assembly of claim 1, wherein the engine firstcomponent and the second component are parts of a combustor liner. 4.The engine component assembly of claim 1, wherein the engine firstcomponent and the second component are parts of a nozzle.
 5. The enginecomponent assembly of claim 1, wherein the engine first component andthe second component are parts of a shroud.
 6. The engine componentassembly of claim 1, said plurality of discrete cooling features havinga polygonal shape in side view, wherein the staggered array is staggeredin both an X and a Y direction.
 7. The engine component assembly ofclaim 6, wherein at least one cooling feature of said plurality ofdiscrete cooling features being one of triangular, square orrectangular.
 8. The engine component assembly of claim 1, wherein eachof said cooling features being positioned near one of said openings. 9.The engine component assembly of claim 1, said cooling features having asurface that is a continuation of at least a portion of a surface of oneof said openings.
 10. An engine component assembly for impingementcooling, comprising: an engine first component having a cooled surface;said engine first component having a flow path on one side of saidcooled surface; an second component disposed adjacent to said enginefirst component between said flow path and said engine first component,said second component having a plurality of openings forming an arraythrough said second component, said cooling flow path passing throughsaid plurality of openings to cool said cooled surface; said secondcomponent having a surface facing said cooled surface of said enginefirst component; a plurality of discrete cooling features extending fromsaid second component surface into a gap between and toward said cooledsurface of said engine first component and defining an array, wherein aforward wall of at least one cooling feature of the plurality of coolingfeatures has a curved cross-section; and, said openings extendingthrough said second component at a non-orthogonal angle to said secondcomponent surface; and, each of said array of said cooling featuresbeing offset from at least one of said opening in said second componentwherein an axis of said opening intersects said cooled surface, andwherein at least one cooling feature of said cooling features has acurved cross-section.
 11. The engine a component assembly of claim 10,said offset being in a second direction, wherein at least one coolingfeature of said cooling features has a cross-sectional area that formsan equilateral triangle.
 12. The engine component assembly of claim 10,wherein the engine first component and the second component are parts ofa deflector.
 13. The engine component assembly of claim 10, wherein theengine first component and the second component are parts of a combustorliner.
 14. The engine component assembly of claim 10, wherein the enginefirst component and the second component are parts of a nozzle.
 15. Theengine component assembly of claim 10, wherein the engine firstcomponent and the second component are parts of a shroud.
 16. The enginecomponent assembly of claim 10, wherein each of said cooling featuresbeing positioned near one of said openings.
 17. The engine componentassembly of claim 10, said cooling features having a surface that is acontinuation of at least a portion of a surface of one of said openings.